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Under-actuated spacecraft three-axis attitude stabilization control method

A stable control method and three-axis attitude technology, applied in three-dimensional position/channel control, adaptive control, general control system, etc., can solve problems such as incomplete drive system

Active Publication Date: 2013-10-02
BEIJING INST OF CONTROL ENG
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Problems solved by technology

The actuators of modern spacecraft attitude control systems mainly use several pairs of jet thrusters or several flywheels or control moment gyroscopes. When working, the failure of any set of mechanisms may lead to the incompleteness of the drive system.

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  • Under-actuated spacecraft three-axis attitude stabilization control method
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Embodiment Construction

[0033] Specific embodiments of the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0034] In order for a satellite (spacecraft) to work normally in orbit, it is generally required to achieve three-axis stable flight, that is, to maintain a certain reference coordinate system, the three-axis attitude angle of the star is controlled near zero, and the nominal value of the three-axis angular velocity is zero. Since the three-axis attitude control of the satellite includes three axes of roll, pitch, and yaw, to achieve three-axis stable control, at least one flywheel is required on each of the three axes, and the attitude of the axis can be controlled by using the flywheel. However, the flywheel has reliability problems. Due to some reasons or long-term work, it may fail, and it may be the first to lose control torque on a certain axis. At this time, only two of the satellite's three axes have the ability to output attitu...

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Abstract

The invention relates to an under-actuated spacecraft three-axis attitude stabilization control method, which designs a controller realizing three-axis attitude stabilization through a two-axis attitude control flywheel in allusion to under-actuated spacecrafts only capable of outputting two-axis control moment. The method comprises the steps of establishing an attitude kinematical equation on the basis of Rodriguez parameters and an attitude kinetic equation in an inertial system; simplifying and organizing the overall system into a Brockett double-integrating system, acquiring a linear control system with controllable system state by adopting sigma conversion and according to whether a starting condition is zero or not, designing a control law to complete the state stabilization of the system, and achieving the purpose of spacecraft three-axis attitude stabilization control. The method provided by the invention can realize three-axis attitude stabilization control when an under-actuated spacecraft only has a two-axis attitude control moment output capacity. Compared with an existing under-actuated control method, the design method provided by the invention is simple, intuitive and easy to implement on stars, and can be applied to three-axis attitude stabilization control of various under-actuated spacecrafts adopting the flywheel.

Description

technical field [0001] The invention relates to a three-axis attitude stabilization control method of an underactuated spacecraft, which can realize the stable control of the three-axis attitude under the condition of only two-axis control moment output, and can be applied to the attitude control of the underactuated spacecraft. Background technique [0002] In the conventional control system of spacecraft, it is usually hoped that the dimensions of the input and output of the system are equal in order to achieve the corresponding control purpose and performance requirements. However, for a system that originally needs to be controlled by several control inputs, can it achieve the same expected control effect with fewer inputs? If feasible, it will increase the reliability of the system and even reduce the cost and weight of the system. Just because of this consideration, it provides a new way of thinking for people to research and develop new control systems. [0003] The...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/10G05B13/04
Inventor 张军邢琰王大轶王南华雷拥军田科丰
Owner BEIJING INST OF CONTROL ENG
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